EP3560817A1 - Antenna assembly for an aircraft - Google Patents

Abstract

The invention relates to an antenna arrangement (3) for an aircraft (1). The antenna arrangement (3) has a structural section (5) of an aircraft (1), an antenna element (16), a cover (13) permeable to radio waves and a structural element (15). The structural section (5) has an arrangement (8) of interconnected longitudinal and transverse stiffening elements (6, 7) and an outer skin (9) which on one side of the arrangement (8) of longitudinal and transverse stiffening elements (6, 7 ) arranged and attached to the longitudinal and transverse stiffening elements (6, 7). A surface of the outer skin (9) facing away from this forms an outer surface of the structural section (5). An opening (12) is formed in the outer skin (9) and is closed by the cover (13). In the area of the opening (12) at least one of the longitudinal stiffening elements (6) and / or at least one of the transverse stiffening elements (7) has an interruption (11) in which the structural element (15) is arranged and which the respective longitudinal or transverse stiffening element (6, 7) divided into two sections (6a, 6b; 7a, 7b) on opposite sides of the interruption (11). The two sections (6a, 6b; 7a, 7b) are connected to the structural element (15) in such a way that tensile and compressive forces act in the longitudinal direction of the respective longitudinal or transverse stiffening element (6, 7), and shear forces act in the transverse direction and torsional forces acting around the longitudinal axis are transmitted through the structural element (15) between the two sections (6a, 6b; 7a, 7b). Alternatively or additionally, the outer skin (9) is connected to the structural element (15) in such a way that shear forces acting in the outer skin (9) are transmitted through the structural element (15) between opposite sides of the opening (12). The antenna element (16) is arranged in the region of the opening (12) on the side of the outer skin (9) opposite the outer surface.

Description

The present application relates to an antenna assembly for an aircraft or aircraft having a fuselage structure section with an array of interconnected elongated longitudinal and transverse stiffening elements and an outer skin, an antenna element, and a radio wave transmissive cover.

Aircraft typically include one or more antennas over which radio communication may be established between the aircraft and external devices or subscribers on the ground or in the air, such as other aircraft or satellites.

In the prior art, such antennas have been mounted, inter alia, on the outside of the fuselage so that they protrude outward from the fuselage into the surrounding air. This increases on the one hand the air resistance of the aircraft, which increases the fuel consumption during operation, and on the other hand, for each type of aircraft, for each antenna and each positioning of the antenna, the aerodynamic pressure and suction forces occurring on the outer surfaces of the antenna, also called aerosol loads be recalculated, resulting in a high calculation and certification effort. In addition, some antenna elements have been attached to the hull via a base plate which has a relatively high weight and projects into the ambient air together with the actual antenna element.

In other embodiments, antenna elements of such antennas have been integrated directly into the outer skin of the fuselage by being provided as a layer of a multi-layer outer skin. In such antennas, however, maintenance and subsequent replacement after fabrication are cumbersome and, in addition, their transmit and receive characteristics may be compromised by deformation of the fuselage or skin during operation of the aircraft.

It is therefore an object of the present invention, an antenna assembly for an aircraft, which is simple and inexpensive, low air resistance of the aircraft allows, is easy to install and maintain, and has a low weight, as well as to provide an aircraft with such an antenna arrangement.

This object is achieved by an antenna arrangement for an aircraft having the features of claim 1 and by an aircraft having the features of claim 15. Advantageous embodiments of the antenna arrangement are the subject of the respective dependent claims.

According to the present invention, there is provided an antenna assembly for an aircraft or an aircraft comprising a structural portion of the aircraft, or more precisely, a structural portion of a structure or sub-structure of the aircraft, an antenna element, a radio-wave transmissive cover, and a preferably rigid one or rigid, structural element.

The structural portion, which may be, for example, a fuselage structure portion of the aircraft or a fuselage structure of the fuselage of the aircraft or a structural portion of a rudder structure of a rudder or wing structure of a wing of the aircraft, comprises an array of interconnected elongate longitudinal and transverse stiffening members. The arrangement of interconnected elongated longitudinal and transverse stiffening elements comprises an elongate longitudinal stiffening element or preferably a plurality, then preferably mutually parallel elongated longitudinal stiffening elements and an elongated transverse stiffening element or preferably a plurality, then preferably parallel to each other extending elongated transverse stiffening elements. The longitudinal stiffening elements or the longitudinal stiffening elements runs or run at an angle to the transverse stiffening element or elements, wherein the longitudinal stiffening elements preferably extend in the longitudinal direction of the aircraft fuselage in the plane of the structural section installed in an aircraft and the transverse stiffening elements in the state of the aircraft Structure section preferably extend in the circumferential direction of the fuselage. The longitudinal stiffening elements are also referred to as stringer and the transverse stiffening elements as frames. The longitudinal and transverse stiffening elements are preferably interconnected in grid form, so that they form an overall grid arrangement. The structural portion also includes an outer skin disposed on one side of the array of longitudinal and transverse stiffening elements - or on one side of the respective grid assembly - and secured to the longitudinal and transverse stiffening elements. This attachment can take place directly without further elements between the outer skin and the respective longitudinal or transverse stiffening element or indirectly via intermediate elements and can be different for different of the longitudinal and transverse stiffening element. For example, it can be provided that the outer skin rests directly on the longitudinal stiffening elements and is fastened directly to them, but that clips are arranged between the transverse stiffening elements and the outer skin, via which the outer skin is fastened to the transverse stiffening elements. In any event, an extended surface of the skin facing away from the longitudinal and transverse stiffening elements and the array of longitudinal and transverse stiffening elements forms an outer surface of the structural portion and, in the aircraft-mounted condition of the structural portion, of the entire aircraft. In other words, the outer skin is arranged and fixed to the longitudinal and transverse stiffening elements such that a first surface of the outer skin faces the array of longitudinal and transverse stiffening elements and a second surface of the outer skin opposite the first surface forms an outer surface of the structural section facing the aircraft in-plane state of the structural section.

The antenna element may be a single unitary antenna element or may comprise an array of a plurality of separate antenna elements that cooperate to radiate and / or receive radio waves.

The cover is permeable to radio waves emitted by the antenna element in operation and radio waves receivable or to be received by the antenna element.

In the outer skin, an opening or passage opening is formed, which may have, for example, a circular, oval, round, polygonal, rectangular or square shape. The opening is closed by the cover, ie the cover is arranged so that it partially or completely fills or completely covers the opening. In the latter case, it should be noted that it is preferable if the cover is arranged on the side of the outer skin is opposite to the arrangement of longitudinal and transverse stiffening elements, ie on the outer surface of the outer skin. But it is also possible to arrange the cover on the opposite side of the outer skin. Further, it should be appreciated that in an arrangement in which the cover only partially fills the opening, the opening may be closed by the cover in combination with one or more further elements, for example, one or more portions of the structural element. In the region of the opening, in each case at least one of the longitudinal stiffening elements and / or at least one of the transverse stiffening elements has an interruption, in which the structural element is arranged and which divides the respective longitudinal or transverse stiffening element into two sections on opposite sides of the interruption. In other words, any such interruption extends completely or partially under the opening, if the outer surface of the structure section is defined as pointing upwards or in a manner perpendicular to the opening, so that the outer skin between the viewer and the arrangement of longitudinal and transverse stiffening elements. All such interruptions together form a coherent interruption or recess in the arrangement of longitudinal and transverse stiffening elements, ie in particular in the corresponding grid arrangement. A contiguous break in a grid arrangement is defined as a region through which none of the longitudinal and transverse stiffening elements passes and which is larger than the normal spaces between adjacent longitudinal and transverse stiffening elements, ie, as the "cells" of the corresponding grid arrangement.

The two sections of each of the longitudinal and transverse stiffening elements, which has one of the interruptions, are connected in such a way, preferably rigidly, to or attached to the structural element that tensile and compressive forces acting in the longitudinal direction of the respective longitudinal or transverse stiffening element , acting in the transverse direction of the respective longitudinal or transverse reinforcing element shear forces and in the respective longitudinal or transverse stiffening element - and, for example, in particular about its strong axis - acting bending moments are transmitted through the structural element between the two sections. In other words, two ends of the respective longitudinal or transverse stiffening element oppose each other on opposite sides of the interruption, ie they define or define the interruption, with the two ends of each of the longitudinal and transverse stiffening elements having one of the interruptions in such a way , preferably rigid, with the structural element are connected, that the described power transmission can take place. In this context, it should be noted that, depending on the orientation and configuration of the longitudinal and transverse stiffening elements in the state installed in an aircraft, not all of the forces and moments mentioned occur during operation or at least do not occur in all of the longitudinal and transverse stiffening elements. If the longitudinal stiffening elements are designed as stringer and the transverse stiffening elements as frames, then, for example, only tensile and compressive forces along their longitudinal axes occur during operation of the corresponding aircraft in the longitudinal stiffening elements, but not shear forces and bending moments, whereas in the transverse stiffening elements all the above-mentioned forces and moments occur and be transmitted by them. Accordingly, the discontinuous longitudinal and transverse stiffening elements are connected to the structural element such that said forces and moments are transmitted between the sections as they occur. The connection between the two sections of the respective longitudinal and transverse stiffening elements and the structural element can be done, for example, by riveting and, for example, directly or via an intermediate element, such as a connection bracket.

Alternatively or preferably, in addition to this connection between the two sections of each of the longitudinal and transverse stiffening elements, which has one of the interruptions, and the structural element, the outer skin is also connected or fastened to the structural element, in the preferred manner rigid, that shearing forces acting in the outer skin are transmitted through the structural member between opposite sides of the opening. It is preferred if the outer skin is connected along the entire circumference of the opening with the structural element in the manner described. For example, the structural element may have an annular portion enclosing an annular opening, and the outer skin may be connected to or secured to the annular portion over its entire circumference. The connection between the outer skin and the structural element can again take place, for example, by riveting and, for example, directly or via an intermediate element, such as a connection bracket.

The structural element is thus a load-bearing element, which is integrated directly into the arrangement of longitudinal and transverse stiffening elements or the outer skin or preferably in the arrangement of longitudinal and transverse stiffening elements and the outer skin, and it is located there is no separate frame around the structural member and the opening mechanically decoupling the structural member from the array of longitudinal and transverse stiffening members with respect to one or more of the above three power transmissions. The structural element at least partially or preferably completely replaces the load-bearing parts of the arrangement of longitudinal and transverse stiffening elements and the outer skin which are missing due to the interruptions or the opening.

It should be noted that the structural element may be connected to a plurality of longitudinal and / or transverse stiffening elements, such that a portion of the forces acting on the section of one of the corresponding longitudinal or transverse stiffening element, on one or more other of the longitudinal or transverse stiffening elements can be transferred or distributed.

Furthermore, it should be pointed out that it is preferable for the structural element to receive the internal pressure prevailing in the interior of the aircraft when it is installed in an aircraft, and in particular to close off the opening in a pressure-tight manner. This can be done by the above-described connection between the structural element and the outer skin is designed appropriately and is provided in particular along the entire circumference of the opening. and by the structural element, the pressure-tight view of the opening seen from the interior of the aircraft. Alternatively, it is possible to provide the cover as a separate pressure-tight closure of the opening, in which case higher demands are placed on the load carrying capacity of the cover, or provide a separate, different from the cover pressure-tight closure of the opening.

The antenna element is in the region of the opening - i. completely or at least partially under the opening, if one defines the outer surface of the structural portion as facing upwards or in the manner described above perpendicular to the opening - arranged on the outer surface or outer side opposite side of the outer skin. In other words, the antenna element is in the aircraft mounted state of the structural portion with respect to the outer skin in the interior of the aircraft.

The antenna arrangement described has the advantage that no heavy base plate is required, since no aerosol acting on the antenna element, so that the antenna assembly can be realized with a low weight. It is also easy to install and maintain. In addition, since the antenna element does not protrude outward from the structural portion, such as the fuselage in the case of a fuselage structure portion, the air resistance is not adversely affected, and the aircraft can have a better visual appearance. Further, unlike embedding an antenna element as a layer in the outer skin of an aircraft, it is easily possible to mechanically decouple the antenna element from the structure and thus avoid deterioration of antenna properties through interaction between the antenna element and loads or deformations in the structure or at least reduce it. Overall, it is possible to retain the advantages of externally mounted antennas, such as ease of installation and maintenance, while still avoiding their disadvantages, especially high air resistance.

In a preferred embodiment, the cover is formed by the structural element. In other words, the structural element is the cover. The antenna element can then be arranged and mounted in any desired manner in the aircraft interior, as long as the radio waves emitted by it during operation pass through the cover from the aircraft and the desired emission direction and the desired emission angle range are achieved. The structural element in this embodiment is preferably plate-shaped and may, for example, have the shape of a flat or, preferably, a curved plate. The structural element may be connected to the two sections of the respective longitudinal or transverse stiffening elements such that the outer skin is arranged between the structural element and the sections or that it bears directly against the sections. In this embodiment, it is possible that the structural element in the above-mentioned manner is connected only to the outer skin, ie not with the longitudinal and transverse stiffening elements, or that the structural element in the manner also mentioned above both with the outer skin and with the longitudinal - And transverse stiffening elements is connected. The latter can for example be realized by the cover rests on an edge region of the outer skin around the opening and is connected in this area, for example by means of riveting to the outer skin, wherein the riveting is designed so that they directly or via intermediate elements and the connection to produces the longitudinal and transverse stiffening elements.

In embodiments in which the cover is formed by the structural element, it is further preferred if the two sections of each or at least some of the longitudinal and transverse stiffening elements having one of the breaks on at their opposite on both sides of the interruption end portions the side facing in the same direction as the outer surface of the outer skin, each having a recess extending to the discontinuity, in which a portion of the structural element is arranged, or a thickening extending to the interruption, with which a portion of the structural element is connected directly or indirectly via an intermediate element. Through the depressions or thickenings, the two sections have, at their ends located on both sides of the interruption, an area of changed thickness, which is separated, for example by a step, from the region of normal thickness of the respective section. If depressions are provided, for example, the structural element, in particular if it is plate-shaped, can be arranged so that it is flush or substantially flush with the outer side of the outer skin, even if the structural element has a greater thickness than the outer skin. In contrast, a thickening can be provided to achieve a local reinforcement in the region of the edge of the opening.

In an alternative preferred embodiment, the structural element and the cover are different components. In this embodiment, it is preferred if at least a portion of the structural element surrounds a receiving space in an annular manner and the antenna element is at least partially disposed in the receiving space. For example, the structural element may advantageously be trough-shaped or annular, wherein the section surrounding the receiving space may have, for example, a circular, round, oval, polygonal rectangular or square shape. In the case of a trough-shaped structural element, the receiving space is formed by the trough interior, and in the case of an annular structural element by the inner ring. But it is also possible to provide an annular structural element and to arrange the antenna element outside of the receiving space. As already mentioned above, in the case of an overall annular structural element, the cover or a separate component must absorb the internal pressure in the aircraft. In contrast, a trough-shaped structural element itself can absorb the internal pressure and close the opening in the outer skin.

In a preferred embodiment, the antenna element is mounted or attached to the structural element or supported by this. As a result, the antenna arrangement can be provided in a particularly simple manner as a unit and the assembly can be simplified. But it is also possible that the antenna element is mounted independently of the structural element in the aircraft interior.

In a preferred embodiment, the antenna element is mechanically decoupled from the structural element. This can be done by providing suitable decoupling mechanisms between the antenna element and the structural element, or by not mounting, mounting or supporting the antenna element on the structural element.

In a preferred embodiment, the cover has a glass, quartz, ceramic or aramid fiber reinforced composite material, in particular, but not only, in embodiments in which the structural element is formed by the cover, for example in monolithic or sandwich construction. Such materials enable the provision of a high load capacity.

In a preferred embodiment, the two sections of each of the longitudinal and transverse stiffening elements, having one of the breaks, are at their opposite end portions on both sides of the break - i. especially locally compared to the rest of each section - reinforced. This can be done for example in the form of the already mentioned thickening or else in other ways, such as by modified mechanical properties. In this way, the power transmission between the sections, with the end portions of the structural element is connected, and the structural element can be improved

In a preferred embodiment, the antenna arrangement further comprises one or more terminals electrically connected to the antenna element for electrical connection to an external unit and / or one or more cable feedthrough openings. The unit may in particular have transmitting and / or receiving electronics, which transmits or receives radio signals with the aid of the antenna element. If a connection is provided, this can - In particular, in embodiments in which the structural element and the cover are separate components - for example, be provided or mounted in an advantageous manner to the structural element. Independently of this, the connection can advantageously be a standard antenna connection or the cable feed-through opening, advantageously a standard cable feed-through opening, so that a standard interface is provided for connection to the on-board electronics of an aircraft, regardless of the exact type of antenna element.

In a preferred embodiment, the cover is plate-shaped and is then formed, for example, in the form of a flat or preferably a curved or curved plate. Alternatively or additionally, it is preferred if an outer side of the cover is flush or substantially flush with the outer side of the outer skin. In this way, the air resistance can be minimized.

In a preferred embodiment, the antenna element is a KU, KA or L-band antenna. The configuration of the antenna arrangement according to the invention generally makes it advantageously possible to provide antenna elements of different sizes and, in particular, relatively large antenna elements on or in an aircraft, for example on or in an aircraft fuselage.

The antenna arrangement according to one of the embodiments described above is part of an aircraft when installed. According to the present invention, therefore, an aircraft is also provided with a structure and an antenna arrangement according to one of the embodiments described herein. The structure has a plurality of longitudinal and transverse stiffening elements and an outer skin. The structural section is part of the structure, ie in particular the longitudinal and transverse stiffening elements of the structural section of the antenna arrangement are part of longitudinal and transverse stiffening elements of the structure. For example, if the structural portion is a fuselage structural portion, the aircraft includes a fuselage and an antenna assembly according to any of the embodiments described herein. The hull then has a hull structure with a plurality of longitudinal and transverse stiffening elements and an outer skin. The hull structure section is part of the hull structure, ie in particular the longitudinal and transverse stiffening elements of the fuselage structure section of the antenna arrangement are part of longitudinal and transverse stiffening elements of the fuselage.

The aircraft may include one or more of the antenna assemblies. It is advantageous that the antenna arrangement can be provided at any point in the aircraft and, for example, at any point in the fuselage of the aircraft, for example at the top, at the bottom or laterally. The same applies to an arrangement on or in other parts of the aircraft, such as a rudder or a wing.

Figur 1

zeigt eine schematische perspektivische Ansicht eines Flugzeugs mit einer erfindungsgemäßen Antennenanordnung,

Figur 2a

zeigt eine schematische perspektivische Ansicht einer Oberseite einer Antennenanordnung gemäß einem ersten Ausführungsbeispiel der vorliegenden Erfindung,

Figur 2b

zeigt eine schematische perspektivische Ansicht einer Unterseite der Antennenanordnung der Figur 2a,

Figur 2c

zeigt eine schematische Querschnittsansicht eines Flugzeugrumpfes mit der Antennenanordnung der Figuren 2a und 2b,

Figur 3a

zeigt eine schematische perspektivische Ansicht einer Antennenanordnung gemäß einem zweiten Ausführungsbeispiel der vorliegenden Erfindung, wobei die Außenhaut zur Illustration weggelassen worden ist,

Figur 3b

zeigt eine schematische Querschnittsansicht der Antennenanordnung der Figur 3a,

Figur 4a

zeigt eine schematische perspektivische Ansicht einer Unterseite einer Antennenanordnung gemäß einem dritten Ausführungsbeispiel der vorliegenden Erfindung, und

Figur 4b

zeigt eine vergrößerte Ansicht eines Teils der Figur 4a.

The invention will be explained in more detail with reference to the figures, in which two embodiments are shown.

FIG. 1

shows a schematic perspective view of an aircraft with an antenna arrangement according to the invention,

FIG. 2a

shows a schematic perspective view of an upper side of an antenna arrangement according to a first embodiment of the present invention,

FIG. 2b

shows a schematic perspective view of a bottom of the antenna assembly of FIG. 2a .

Figure 2c

shows a schematic cross-sectional view of an aircraft fuselage with the antenna arrangement of FIGS. 2a and 2b .

FIG. 3a

shows a schematic perspective view of an antenna assembly according to a second embodiment of the present invention, wherein the outer skin has been omitted for illustration,

FIG. 3b

shows a schematic cross-sectional view of the antenna arrangement of FIG. 3a .

FIG. 4a

shows a schematic perspective view of a bottom of an antenna assembly according to a third embodiment of the present invention, and

FIG. 4b

shows an enlarged view of a part of FIG. 4a ,

This in FIG. 1 Aircraft 1 shown has a fuselage 2 and an antenna arrangement 3 according to the invention. In addition to the antenna arrangement 3, conventional leaf antennas 4, which are fastened to the fuselage 2 from the outside and protrude outward from the fuselage 2, are also shown for illustration purposes. In contrast, the top of the antenna array 3 is flush or substantially flush with the surface of the fuselage 2, so that the aerodynamic drag of the fuselage 2 is not or not substantially increased by the antenna array 3 and no or substantially no increased aerosol effects on the antenna array. In the FIG. 1 For example, the antenna arrangement 3 is arranged on the upper side of the fuselage 2 by way of example. However, the antenna arrangement can also be located at any other location of the fuselage 2, for example at one side or at the bottom. The hull 2 has in the usual way a hull structure with a lattice-shaped arrangement of interconnected longitudinal and transverse stiffening elements, on which an outer skin is arranged (for the aircraft in FIG. 1 not shown separately). As can be seen from the further figures, the antenna arrangement 3 has a fuselage structure section or a fuselage structural element 5, which is part of the fuselage structure of the fuselage 2 and can be integrally formed with the fuselage structure of the fuselage 2 or integrated into it as a separate component , It should be noted that the antenna assembly 3 can also be provided at locations other than the fuselage 2, such as the rudder or a wing. By way of example only, the figures show the arrangement on the fuselage 2. In an arrangement elsewhere, instead of the fuselage structure section 5, a structural section of the corresponding substructure of the aircraft is provided, such as a rudder structure section or a wing structure section.

The FIGS. 2a to 2c show a first embodiment of the antenna assembly 3. The antenna assembly 3 has a body structure element 5, the structure of which is more precisely apparent from the figure 2b. On the one hand, the fuselage structural element 5 has a plurality of longitudinal stiffening elements 6 and a transverse stiffening element 7, which are interconnected and together form an assembly 8 of longitudinal and transverse stiffening elements 6, 7. The longitudinal stiffening elements 6 extend in the longitudinal direction of the hull 2 when installed in the hull 2, and the transverse stiffening element 7 extends into Circumferential direction of the hull 2 perpendicular to the longitudinal stiffening elements 6. On the other hand, the hull structure element 5 has an outer skin 9, which is arranged on one side of the assembly 8 and secured thereto. An outer surface 10 of the outer skin 9 forms a part of the outer surface or the outer side of the fuselage 2 when installed in the fuselage 2. The arrangement 8 is located on the side of the outer skin 9 opposite the outer surface 10.

An interruption 11 is provided both in the transverse stiffening element 7 and in two of the longitudinal stiffening elements 6, dividing the respective longitudinal or transverse stiffening element 6, 7 into two respective sections 6a, 6b or 7a, 7b on both sides of the interruption 11 , All three interruptions 11 together define a continuous interruption in the assembly 8, and in this continuous interruption an opening 12 is formed in the outer skin 9 (see FIG FIG. 2b ). This opening 12 is pressure-tightly closed by a cover 13, which is formed in the form of a curved plate and disposed on the side of the outer surface 10 on the outer skin 9 and the opening 12 completely covered. In this case, a peripheral edge region 14 of the cover 13 extends over the entire circumference of the opening 12 beyond this, so that it overlaps with a part of the adjacent to the opening 12 outer skin 9. In this edge region 14, the cover 13 is attached to the outer skin 9 and through this or via these at the opposite portions 6a, 6b and 7a, 7b of the interrupted longitudinal or transverse stiffening elements 6, 7. But it is also possible that the cover 13 is attached only to the outer skin 9.

In this exemplary embodiment, the cover 13 of the antenna arrangement 3 simultaneously represents a load-bearing or load-transmitting structural element 15, by the longitudinal forces acting along the longitudinal or transverse reinforcement elements 6, 7 acting transversely to the longitudinal or transverse reinforcement elements 6, 7 Shearing forces and torsional forces acting around the longitudinal direction of the longitudinal or transverse stiffening elements 6, 7 are transmitted between the sections 6a, 6b and 7a, 7b of the interrupted longitudinal and transverse stiffening elements 6, 7. In this way, a weakening of the fuselage structure in the region of the antenna arrangement 3 can be avoided or at least minimized.

Finally, the antenna arrangement 3 has an antenna element 16 (see Figure 2c ), which is arranged on the outer surface 10 of the outer skin 9 opposite side of the outer skin 9 and is therefore located in the fuselage 2 built or integrated in the interior of the fuselage 2 of the aircraft 1. The arrangement of the antenna element 16 in the interior of the fuselage 2 is essentially arbitrary as long as the radio waves radiated and received by the antenna element 16 with the desired emission angle range 17 can pass through the opening 12 and the cover 13, 15. The cover 13, 15, which itself is designed as a load-bearing structural element 15, is permeable to the radio waves and may for example consist of or comprise a glass or quartz fiber reinforced composite material. The antenna element 16 can be mounted independently of the fuselage structure section 5 and the fuselage structure of the fuselage 2 in the aircraft interior, so that it can be mechanically decoupled from loads and deformations of the fuselage structure and the fuselage structure section 5.

The FIGS. 3a and 3b show a second embodiment of the antenna assembly 3, in which, unlike the FIGS. 2a to 2c the cover 13 and the structural element 15 are separate elements or components. The structural element 15 is formed trough-shaped, so that it defines a receiving space 18. The antenna arrangement 3 of the FIGS. 3a and 3b has a fuselage structure element 5, the structure of which the FIGS. 2a to 2c corresponds, so that reference is made to the above explanations. In the FIGS. 3a and 3b In this case, only a number of three transverse stiffening elements 7 are shown, one of which has an interruption 11. In this interruption 11, the opening 12 is formed in the outer skin 9 (see FIG. 3b ), and the opening 12 is again closed by a cover 13, which is formed in the form of a curved skin and in its edge region 14 circumferentially attached to the structural element 15.

In contrast to the embodiment of FIGS. 2a to 2c However, the cover 13 is not formed load-bearing or need not be designed load-bearing. For the purpose of transmitting longitudinal forces acting along the discontinuous transverse stiffening element 7, transverse and shear forces acting transversely to this transverse stiffening element 7 and bending moments acting in the transverse stiffening element 7 between the sections 7a, 7b of this transverse stiffening element 7 and for transmission in the outer skin 9 Shearing forces between opposite sides of the opening 12 rather the structural element 15 is provided and adapted, which is directly rigidly connected to the outer skin 9 with ends 19a, 19b of the two sections 7a, 7b of the interrupted transverse reinforcement element 7 and around the entire circumference of the trough opening. The transmission of force and torque between the sections 7 a, 7 b and the transmission of force between sections of the outer skin 9 on opposite sides of the opening 12 is thus effected via the structural element 15 independently of the cover 13.

The structural element 15 has at its upper edge a bent, circumferential flange portion 21, with which it rests from below on a directly adjacent to the opening 12 peripheral edge region of the outer skin 9 and on which the outer skin is fixed, for example by rivet joints 25, such as she in the FIGS. 3b and 4b are shown. This makes it possible for the cover 13, which in this example is fastened with its edge region 14 to the flange section 21, to be flush or substantially flush with the outer surface 10 of the outer skin 9.

In the receiving space 18 of the structural element 15, the antenna element 16 is arranged, which is thus in relation to the outer skin 9 in the installed state in an aircraft 1 inside the fuselage 2 of the aircraft 1.

The opening 12 is closed by the structural element 15 pressure-tight from the inside, so that the structural element 15 receives the pressure prevailing inside the aircraft internal pressure. In contrast, the closure of the opening through the cover 13 in this embodiment only serves to ensure the smoothest possible outer surface of the antenna arrangement or surface of the aircraft.

The FIGS. 4a and 4b show in a schematic perspective view from below a third embodiment of the antenna assembly 3, which largely corresponds to the second embodiment of the FIGS. 3a and 3b like. The only difference is that several longitudinal stiffening element 6 have an interruption 11 and that the sections 6a, 6b and 7a, 7b of the interrupted longitudinal and transverse stiffening elements 6, 7 are each connected via a rigid connecting piece 22 with lugs 23 on the structural element 15 , In the FIGS. 4a and 4b It can also be seen that in the bottom of the trough-shaped structural element 15, a cable feedthrough opening 24 is provided, through which a cable for connecting a transmitting and / or receiving electronics to the antenna element 16 can be passed.

Claims (15)

Antenna arrangement for an aircraft (1), the - A structure section (5) of a structure of an aircraft (1), the - An arrangement of interconnected elongated longitudinal and transverse stiffening elements (6, 7) and - Has an outer skin (9) on one side of the assembly (8) of longitudinal and transverse stiffening elements (6, 7) arranged and fixed to the longitudinal and transverse stiffening elements (6, 7), wherein a surface facing away from these Outer skin (9) forms an outer surface of the structural portion (5), an antenna element (16), - A radio wave permeable cover (13) and a structural element (15), wherein in the outer skin (9) an opening (12) is formed, which is closed by the cover (13), and in the region of the opening (12) at least one of the longitudinal stiffening elements (6) and / or at least one of the transverse stiffening elements (7) an interruption (11) in which the structural element (15) is arranged and which separates the respective longitudinal or transverse stiffening element (6, 7) into two sections (6a, 6b; 7a, 7b) on opposite sides of the interruption (11) divided
wherein the two sections (6a, 6b; 7a, 7b) are connected to the structural element (15) in such a way that tensile and compressive forces acting in the longitudinal direction of the respective longitudinal or transverse reinforcing element (6, 7), transversely acting shear forces and torsional forces acting around the longitudinal axis are transmitted through the structural element (15) between the two sections (6a, 6b; 7a, 7b), and / or wherein the outer skin (9) is connected to the structural element (15) in such a way shearing forces acting in the outer skin (9) are transmitted through the structural element (15) between opposite sides of the opening (12), and
wherein the antenna element (16) in the region of the opening (12) on the outer surface opposite side of the outer skin (9) is arranged. Antenna arrangement according to claim 1, in which the cover (13) is formed by the structural element (15). Antenna arrangement according to Claim 2, in which the structural element (15) is plate-shaped. An antenna arrangement as claimed in claim 2 or claim 3, wherein the two sections (6a, 6b; 7a, 7b) of each of the longitudinal and transverse stiffening elements (6, 7) having one of the breaks (11) at their on both sides the interruption (11) opposite end portions on the outer surface side facing each extending to the interruption (11) extending recess in which a portion of the structural element (15) is arranged, or extending to the interruption (11) thickening have, with which a portion of the structural element (15) is connected. An antenna assembly according to claim 1, wherein the structural member (15) and the cover (13) are different components. An antenna arrangement according to claim 5, wherein at least a portion of the structural element (15) annularly surrounds a receiving space (18) and wherein the antenna element (16) is at least partially disposed in the receiving space (18). Antenna arrangement according to Claim 6, in which the structural element (15) is trough-shaped or annular. An antenna assembly according to any one of the preceding claims, wherein the antenna element (16) is mounted to the structural member (15). Antenna arrangement according to one of claims 1 to 8, wherein the antenna element (16) is mechanically decoupled from the structural element (15). Antenna arrangement according to one of the preceding claims, wherein the cover (13) comprises a glass, quartz, ceramic or aramid fiber reinforced composite material. Antenna arrangement according to one of the preceding claims, in which the two sections (6a, 6b; 7a, 7b) of each of the longitudinal and transverse stiffening elements (6, 7), the one of the interruptions (11), are reinforced at their opposite on both sides of the interruption (11) end portions. Antenna arrangement according to one of the preceding claims, further comprising at least one connection electrically connected to the antenna element (16) for electrical connection to an external unit and / or at least one cable feed-through opening (24). Antenna arrangement according to one of the preceding claims, wherein the cover (13) is plate-shaped and / or in which an outer surface of the cover (13) is flush with the outer surface (10) of the outer skin (9). Antenna arrangement according to one of the preceding claims, in which the antenna element (16) is a KU, KA or L-band antenna. An aircraft comprising a structure and an antenna assembly (3) according to any one of the preceding claims, wherein the structure comprises a plurality of longitudinal and transverse stiffening elements (6, 7) and an outer skin (9) and wherein the structural portion (5) is part of the structure ,

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